Stabilizer for aeroplanes.



A. B. THAW.

STABQLIZER .FOR AEROPLANES. APPLICATION men v4.24. ma.

' Patented oet. 26,1915.

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Alexander B/q/i' Thm v A. B. THAW STABILIZER FOR AEROPLANES. r APPLICATION FILED Mt 4.24.1913. 1,158,333. I PatentedOct. 2 1915,

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A. B. THAW.

STABILIZER FOR AERGPLANES.

APPLICATION FILED JAN.24.1913.

Patented Oct. 26, 1915.

4 SHEETS-SHEET 3- I IN VE IV TOR Alexander B/a/I' T/m'w WITNESSES ATTORNEYS A. B. THAW. STABILIZER FOR AEROPLANES. I APPucmon min JAN. 24. 19,13. 7 1,158,333. v Patented Oct. 26, 1915.

4 SHEETS$HEET 4- I M i I vide a mechanlsm of the character men- UNITEn STATES PATENT OFFICE.

annxannnannam :rHAw, or rrrrsnimsn, PENNSYLVANIA.

STABILIZER AEROPLANES.

To all whom it may concern:

Be it knownthat I," ALEXANDER BLAIR THAW, a 'citizenof the United States, and a resident of Pittsbur h, in thegcount of Allegheny and State 0% Pennsylvania, ave invented a new and Improved Stabilizer for Aeroplanes, of which the. following is a full, clear, and exact description.

Among the principal objects which the present invention hasin view are: to protioned to selectively operate in accord with thev list or tilt of the aeroplane by which it is carried; to rovide a mechanism of the character named with a wind motor operable by the pressure of the air through which the aero lane is passing; to provide in a machine 0 the character named, means operative concordant with the-steering mechanism of an aeroplane, to maintain the ratio of stability at various inclinations of the aeroplane; to provide a universal stabilizer;

: to provide means for varyingthe ratio of the aeroplane.

- stabilization; and to prov de means for varying the ratio of stabilization-relative the longitudinal and transverse dimensions of One embodiment of the present invention is shown in the accompanying drawings, in which-.

Figure 1- is a sectional elevation of a stabilizer constructed in accordance with the.

present invention; Fig. 2 is. a vertical cross section taken on the line 22 in Fig. 1; Fig. 3- is a plan view of the stabilizer; Fig. 4 is a detail view, on an enlarged scale and in vertical section, showing one of the electrical contact posts with which themachine is equipped; Fig. 5 is a diagrammatic view showing the electrical wiring and selective contacts forop'erating the various elements of the stabilizing mechanism; Fig. 6 is a diagrammatic "view showing theifelectric Fig. 6; Fig.8 is'a genera-lvview,showing an aeroplane and the present stab liz ng ma;

thereon/ wiring and selective, contacts for operating the various elements of the stabilizing mechanism, constructed-and arranged, in accordance with a modification of the present invention; Fig. 7' ,is a detai'lview, on an en- 'larged scale, showing the. upper fragment of a connector such as used in conjunction, with the modlfied-iform ofw1r1ng shown n.

chine "as mounted in operative position As seen in the 4 suit able tr-ipod'38. drawings, and particularly t Patented Oct. 26, 1915..

Fig. 8 thereof, the herein-disclosed stabilizer is connected with warping sections such as A and B, and with a. levitating rudder C. Said warping sections A and B are connected to drums 14 and 15, respectively, whlle the levitating rudder C is operatively connected to drums 16 and 17 at the lower and upper side thereof, respectively. The drums are suitably mounted in standards erected upon a base plate 18, which, is suitably mounted upon one of the carrying planes of the aeroplane. The above connections are effected by cables 19, 20, 21 and 22,3"arranged substantially as shown in 8 of the drawings. I he' drums 14.to 17 v inclusive are mounted on sleeves held rigidly in standards 23, 24 and 25. As seen best in Fig. 1 of the drawings, the drums 14 and 15 are mounted each on a sleeve 26, the outer end whereof is flanged to hold the hubs 27 of said drums in bearing relation with the face of said standards 23 and 25. The centralstandard 24 holds two short sleeves 28, the 'flangdt go ends of which hold the hubs of the, drums 16 and 17 in bearing relation to the faces of are alined to'lform the standard 24. Each of the standards 31, with whichis meshed a worm 32. The

pitch, of the worm and worm wheel and the ratio therebetween arevarled to accommodate the amount of rotation in speed de-' sired between the vertical driving shaft'33 and the shaft 30,-the intention being that the shaft 30 shall rotate relatively slowly.

The shaft 33, is vertically disposed and suitably mountedin bearings in the base plate 18. The shaft is. rigidly connected with tl1e,wor1n32,'and at the lower end with a 1111534, from which are ektendedyarms35 supporting each at its. ol'itel extremity an anemometerlcup 36. The length ofthe arms 35 {and the number of arms and 'cu-ps emplo ved 1nay' be a varied to suit the conditions or desire of the owner. ,The air motor thus formed is relied, uponjto drive the "shaft the .lowerj end whereof is in'o steadiiing bearing 37' at thelow It will be' u'ndei'stood that whil e the air motor .above described is shown in the ac,

' motor may.

' shafts 33 and shaft 33: and the air motor may companying drawings as disposed bclowthe stabilizer, herein disclosed, it may, if the design compels such an arrangement, be located at any suitable station on the aero-.

Likewise, the disposition ofthe air be varied in a vertical plane rather than in the horiplane.

zontal as shown in the drawings. Proper transmission mechanism connecting the of the fact of the operation of the'propelling motor. In other words, the shaft is rotated during the gliding periods of flight of the aeroplane.

Mounted upon the shaft- 30, to rotate therewith, are two double-faced clutches 39 and 40. Elongated feathers or splines 41 are provided, to govern said clutches when This moved lengthwise of the shaft 30. movement is imparted by clutch yoke levers 42 and 43. The ends of the yokes of the levers 42 and 43 are provided with pins to extend into grooves 44, with which said clutches are provided. The clutch levers 4'2 and 43 are pivotallv mounted on pins --,The lower end of each of said levers is provided with a cross bar soft iron armature 46 extending between the cores of magnets 47 and within' the magnetic area thereof. The

one or two of the same levers 42 and 43 are held centrally disposed by springs 48.

-'The magnets 47 are operated selectively,

being energized coincidentally in accord with the tilting of the base plate 18. The, various magnets are operated by a suitable battery mounted in'a battery-box base plate 18.

which is rigidly secured to the One leg of the circuit of each ofthe magnets '47 includes one of the tube caps 50. The opposite leg of the'circuit of each magnet, incorporates oneof the tubes 51 and the mercury 52 contained therein. Each of the; tubes 51 has a vertical section 53. In the normal or horizontal position of the base plate 18, the mercury 52 in each of the vertical sections 53 of the four tubes 51 is at the Same level and on a level with the top of the mercury in tube 51. In this'position 0f the base plate and mercury contained in the tubes 51, the space between said mercury and the needle 54 in each of the tube caps is the same. This space may be varied to yauit-thedesires of the aviator, to render the -m' achi'ne rigid or It will be understood that when the aerolane carrying the stabilizer is tilted inits transverse or longitudinal plane,

flexible in its stabilization.

to incline mercury 52 1110116 the base plate 18 until the 53 makes contact of the vertical sections with the needle 54 of one of the tube caps 50, I

so that the cups rotate the electric circuit sum-e133- e'stahlishcd in one of the magnets 47. The energized magnet draws to it the. armature i with which it corresponds, rocking'the lever 42 or 43, as the case may be, to throw the clutch 39 or 40 connected therewith.

The clutches 3!) and it) are each provided on the opposite faces with truncated teeth 55 which engageithe spokes of the drums M to 17 inclusive. It will be understtxid that any suitable form of clutch may lie'employed. The elect ric circuits are so arranged that the tube caps 50 transversely disposed relative the longitudinal axis of the aeroplane operate the magnets +7 to throw the lever-s42 and 4 to engage the drums connected with the warning sections and B. A further arrangement insures that the tube cap on one sideof the longitudinal centerwitihe base-plate as disposed on ,the aeroplane, operates the magnet which afl'ects the warping section on the same side ofsnid longitudinal center. Likewise, the caps 50 longitudinally disposed on the plate 18 and aeroplane are ating to control' the drums which are connected with the levitating rudder C, and these longitiuliinilly-disposcd caps are selectively arranged tooperate the cahles2l and 2'. arranged to iuclinethe rudder upward and downward, respectively.

From the foregoing, it will be seen, that with the caps 50 set to govern the free the aeroplane, thereafter 'thewarping sections A and B and the levitating rudder C will be automatically adjusted to correct the tilt of the aeroplane whenever the list extends beyond the limit set therefor, and by reason of the fact that the electric circuit is establishedin the proper magnet 47 to throw the clutch on the shaft 30 to engage the proper drum 14, 15, 16, or 17, to cause the same to rotate with said shaft 30 mg in the inclination of one or the other said warping sections of 'the carrying plane or the uplifting or depression of the rudder C.

serving as a guide for the tube on 50nd to 'form an electrical contact t ere'lvith. The collar 59-is suitably mounted at thb up per end of a bracket 60, the foot of which rests upon an insulating pad 61, and is provided with a binding post 62 to receive o incorporated in circuits operthis result- Fig. 4 oftilt of wheels fixedly mounted upon a transmission wire terminal1.63; directly connected with one ofthe, magnets 47, see Fig. 5 of the drawings.

' a""fixed bevel'gear wheel 65. The gear wheel 65 is meshed with a mated gear wheel (ififor'ming one of a pair ofcorrespondmg shaft 67'. The shaft 67 has hearings in the vertical edge flange of the base plate 18, and is provided at the outerside of. said flange with a pulley 68.

"There are two shafts 67, each connecting, by means of the gears 66, the oppositelylocated shafts 64and-bevel wheels 05 .connected therewith. Each of the pulleys (i8 is operatively connected, preferably by auxiliary belt loops. 69, with the controlling levers or ftiller posts of the aeroplane.

A predetermined amount of slack in theauxiliary loops (5!) is provided, the purpose being to. permit the controlling levers, or the tiller, to be operated to a predetermined degree before the pulleys '68 and partszco'nnected therewith are affected; The

purpose in this construction is to provide for lifting theneedles 5under certain opcrating conditions of the aeroplane, such as, for instance, when banking or turning a .sharp curve. The shaftjfi'i and its pulley In other words,- when a stabilizer is thus The nuts 56,- being 68 which extends between the caps'fiO disposed ti'ansversely'in the aeroplane, is connected with the rigging for ,controlling the rudderfor steering the ae roplane in. a horizontal plane. The -s'hztft (i7 amlpulley:v 68 for operating the longitudinally-disposed caps 50 are operatively connected with the rigging for varying the levitating rudder (Y I When either of the shafts 67 is rotated, it will be-seen, the wheels and shaft 6'4 connected therewith are rotated and equally rotated'at opposite sides of the base plate 18.

rigidly anounted on the shafts 64, are similarly rotated. I The caps 50, bein held againstrotation by the'fins 158, are lifted or depressed, as'the case may sa|'ne length: that is. the needles 71in each 115 be, by the operation of the nuts 56.

The result of the action above set forth is that the space between the mercury 52 contained in each of the tubes 51 and in'the sections" 53' thereof, and the; needle 54, is'varied to suit' 'the above-mentioned conditions arrived atfin the operation of the; aeroplane.

equipped, iikthe aviator ,desiresito bank his machine, by throwing theruddento' tnrnya sharp curve and at the same time manually manipulate-the warping planes-a to liftone;

side thereof, the corresponding shaft 67 is rotated to lift the caps 50 operatively con nectedv therewith to increase. 'the space between the need les 7 54; and .the mercury con.-v

The nut 56 above referred to; rigidly "under call) connected with A wiper 86 is connect inch of the tubes 51 is electrically connected with one of the magnets-l7. and ,all of the magnets are electrically connected one of the sections is ..with the needle 71 the circm through the magnet '47 orresp the particular: tube -51 in 'whicl' 'ls mad, provided the Wheel havl jtion' 81 is turned-to form-mama taincd in the sections 53. By'sctting the rigging for controlling the aeroplane in its will be seen that during the banking, or what may be termed the incidental position of the aeroplane, the safety factor of varying the inclination is preserved by means of'the present stabilizer, which will operate from the position set to accommodate the banking as readily as from the position set to accoimnodate the sailing on a level plane. 4

In Fig. 7 is shown a modified form of the contact terminals. The modification consists in that the sections 53 are provided with an internal screw thread atthe upper end to receive a screw-tln'caded plug 70. The plug is constructed from insulating material, and is of a len th to admit of insertion or withdrawal from the section 53.

Three needles 71, 72 and I? are extended throughthe plug 7(l, cxtending from the surface thereof to varying degrees.

'hen the' plug is screwed into the section o3, it Will be seen by relcrcncc'to Fig. '7 of the drawings that the space separating the needles from the mercury 5:2 in each case varies.

The needles are provided with binding posts 74, 75, andi'fi. to which are connected terminal wires 77. 78 and' 7!). 4 i 78 and 79 connected with each 70 are united in a common ground and electricallv connected to a wiper 80. The wipers S0, S5 and -86. as seen in the diagram Fig. ii

of the drawings, are clustered about a disk orwhecl, which wheel is provided with'an clectro-conductive section 81 and a non-coin dilctive section 82. net-ted with the terminal 83 of a battery Hi.

"hcn the wheel ha ving thesections and. 1 l7) 82 is rotated, the various wipers are successively placed in circuit with'the battery 84.

Each of the wipers is electrically connected with all of the needles 71. T2 and T3 of the of the tube sections 53 are connected with the wiper 0. Two *wi ers 85 are each electri- \'\ill of, the needles T2.

el with all of the neeto a return wire or ground 87. Thus, it will be seen that whenever ondin the stic between The wi res Td'g', 1 C1) of the plugs The section 81 is conneetire gearing.

said section .a "d the wiper corresponding with the partic jneedle. In other words, if the lllel'cill') 32' is raised in, the tube sec tion- 5:5.to contact with the needle 71, the circuit will be completed through one of the magnets 17. provided the wiper 30 is in contact withth'c section 81 of the rotary wheel as shown in Fig. '6 of the drawings. It wili be noted in this figure thatthe heavy black lines indicate the circuits including the needies-T1. while the light line's include the circuits embodying the needles T2 and 73.

If, by the operation of the steering levers. of the aeroplane.the loop 88 of the steering rigging be manipulatedfto rotate the section H1. to contact with the wiper then it will be noted that the circuits embodying the needles T1 and "2 H0 and H5 being in contact with the insulating seetionfi'. of said wheel. The mercury .32 may under these conditions. rise into contact with the needles T1 and 72, without energizing themagnets W. 'hen. however, the mercury rises to contact with the needle 7;). the electric circuit is completed through are broken. the wipers one of the magnets. thereby energizing the I same to operate the stabilizer.

It will he noted that there are two wipers 5.). -ln this mannerprovision is made for turning the disk or wheel having the sections 'l and 1. in either direction. to emplov-the needle T1! equall when banking to the right or lnrnl tiiig to the left.

lt will=la observed that as the mechanism.

bort-T desi-ribed provides for a continuousl operating'driving shaft and temporary engage: its'therewith for 'each of the winding drums li 'i'ii 17 inclusive. the contact between the {shaft and the drums might be continued beyond the flexing limit of tile ailerons or warpingsections. This would necessarily result in-l realmge of the aeroplane or con- 'lo avoid such a contingency. l have provided spring brushes 8!), which are mounted on the frame of the machine ain't insulated therefrom. Said brushes are connected with their respective magnets by means of wires 90. The brushes bear against tlie peripheries ofthe flanges of the drums H'to li.respeetivel v, which, at a certain portion are provided with an insulating section 91. from said magnets to the battery contains the spring brushes 89. The operation, when thus equipped. of the drums, provides for less than a whole revolution of said drum.

When. in theoperation. the insulating section 91 passes under the spring brush 89, it wiil be seen, the circuit is broken in the magnet holding the levers 42 and 43,'permitting the springs controlling saidleverto retract the clutelies-,39 and -L0 from engagement with the drum atthe I moment operating, 'Jhepressm-e of the warped or inclined section or aileron immediately retracts the The leg of the circuit result of rengagement with the clutch, of

the drum. in operation." By this means, it will be seen, the mechanism is saved from the results of the drum making more than ti complete revolution. While I have-herein described the stablvthrough the magnet, with the consequent 1 liver as employing a motor for operating the shaft 30,- it will,be understood that I may employ an electric motor, compressed air admitted to cylinders whenneeded, from a reservoir.- or other suitable prime mover. pref erablv independent of the propelling. power for the aeroplane.

Having thus described my invention, I claim as new and desire to secure by Letters Patent 1. In combination with an aeroplane having a plurality-of righting members, a stabilizer. comprising a shaft; a wind motor for continuously driving said shaft; a plu rality of winding devices, each operatively connected with one of said righting members; a plurality of electro-mechanically a ctuated' connectors foi-operatively connecting said shaft and said winding devices successively: and a plurality of self-leveling circuit-closers, each adapted to close the circuit of onef'of said connectors.

2. In combination with an aeroplane hav ing a plurality of righting members, a stab ilizer. comprising a plurality of winding memberszfa motor adapted to be operated' by the pressure of air'through which the aeroplane travels; means for temporarily connecting said motor and winding devices successively; electro-mechanically-operated clutches for connecting said motor and winding devices; and circuit-closers for actuating the mechanism controlling said clutches,

said closers having columns of mercury and containers therefor, wherein the mercury relatively rises as the side of the aeroplane supporting the same is lowered.

3. A stabilizenhaving a continuously-operating shaft; a plurality of winding drums mounted on said shaft; :1 pluralityof electro-magnets for connecting said shaft and said drums; a pluralityof electric circuits, each incorporating one of said magnet-sand an electric source; a plurality of bent mercury-containing tubes, each having a portion disposed perpendicular to the horizontal of the aeroplane, each of said tubes being incorporated in one of said circuits; a plurahty'of contact member s,' one movably mounted in each of said tubes, above the .mercury therein"; a plurality of mechanisms, I each adapted to lift said contact member in said tube to vary the separation-of said member and said mercury, in the normal position of said aeroplane; and-means'op-J 'eratively connecting said mechanisms avith the controlling gear of said aeroplane.

3 perpendicular vertical planes; a 1'0 to cover one of said bent tubes; a contact 4 .-In a stabilizer such as described; a plurality of. e1ectro-a ctuated operatingmecha- -nisms,-*einbodying normally open circuits; a plurallty of bent mercury-containing tubes,

said tubes being arranged in pairs and spaced'a-part, said pairs being disposedin plurality of inverted tubes, each telescopically arranged needle mounted on each inverted tube to extend within said benttube for immersion 1n the mercury therein a plurality of rotary members mounted W1th1n sa1d inverted pairs to move in unison;vand means operatlvely connecting each of sald pan-s with the controlling mechanism of the aeroplane to move in predetermined relation therewith.

In testimony whereof I have signed my name to this specification in the, presence of two subscribin witnesses.

ALE 'ANDER BLAIR THAVV. \Vitnesses: 1 E. F. MURnocK,

ELMA Dows THAW. v 

